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针对大气制动轨道转移过程中出现的近心点下降问题,给出了一种利用气动力实现近心点高度控制的方法.设计了以倾侧角为控制变量的大气内飞行控制律,并参考相关星际探测任务进行了仿真验证.通过改变倾侧角调整气动力在高度方向上的分量来实现对制动轨道近心点高度的控制,并根据当前近心点高度与预定近心点高度自动调整反馈增益.在整个大气制动过程中本方法无需燃料消耗即可有效地限制近心点下降并最终减少下降量,同时使飞行过程中的最大动压和最大热流密度逐渐降低,保证了航天器的安全.
Aiming at the descent of the near-center point during the process of atmospheric braking orbit transfer, a method of using aerodynamic force to achieve the near-point height control is given. The control law of the flight with the tilting angle as the control variable is designed. Related interstellar exploration missions were simulated and verified.At the same time, the height of the brake track was controlled by changing the tilting angle and adjusting the components of the aerodynamic forces in the height direction, and the height of the brake track was automatically adjusted according to the current height of the center point and the preset height of the center of gravity Feedback gain.The method can effectively limit the decrease of the centripetal point and reduce the descending amount effectively without fuel consumption during the entire atmospheric braking process and at the same time gradually reduce the maximum dynamic pressure and the maximum heat flux during the flight so as to ensure that the spacecraft Security.